TCDS A29EU

Page No. 1 2 3 4 5 6 7 Rev No. 7 3 3 3 6 3 3 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A29EU Revision 7 Britten-Norman Aerospace, Ltd. BN2A MK. III BN2A MK. III-2 BN2A MK. III-3 April 11, 2024 TYPE CERTIFICATE DATA SHEET NO. A29EU This data sheet, which is a part of type certificate No. A29EU, prescribes conditions and limitations under which the product for which the type certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder Britten-Norman Aerospace Ltd Bembridge Airport Isle of Wight, PO35 5PR, United Kingdom Type Certificate Holder Record Britten-Norman (Bembridge) Limited transferred TC A29EU to Pilatus Britten-Norman Limited on Septermber 24, 1979. Pilatus Britten-Norman Limited transferred TC A29EU to B-N Group Ltd. on December 9, 2002. B-N Group Ltd. Transferred TC A29EU to Britten-Norman Aircraft Ltd. on January 12, 2023. Britten-Norman Aircraft Ltd. transferred TC A29EU to Britten-Norman Aerospace Ltd. on April 11, 2024. I. - Model BN-2A MK. III Trislander, 18 PCLM (Normal Category), Approved 4, August 1971 Engines 3 Lycoming O-540-E4C5 (See NOTE 6) Fuel 91/96 Minimum grade aviation gasoline Engine limits For all operations, 2,700 r.p.m. (260 hp.) Propeller and Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, Hartzell propeller limits HC-C2YK-2C/C8477-4, Hartzell HC-C2YK-2C/C8477A-4 and Hartzell HC-C2YK-2CF/FC8477A-4 (See Note 5). Diameter range 80" maximum, 78" minimum. No further reduction permitted. Pitch setting at 30 in. station: Low 12.5° High 78.6° Spinners: Hartzell 836-29 Governors: Woodward 210275, D210659, 210715, F210444, G210659, or B210715 (See NOTE 7) Airspeed limits (IAS) With Modification NB/M/510 airspeed indicator installed Vne (Never exceed) 195 knots (225 m.p.h.) Vno (Max. structural cruising) 152 knots (175 m.p.h.) Va (Maneuvering) 130 knots (150 m.p.h.) Vfe (Flaps take-off) 113 knots (130 m.p.h.) Vfe (flaps landing) 106 knots (122 m.p.h.) Vmc (minimum control) 50 knots ( 58 m.p.h.) With Modification NB/M/501 airspeed indicator installed Vmo (Max. operating limits) 152 knots (175 m.p.h.) Va (Maneuvering) 130 knots (150 m.p.h.) Vfe (Flaps take-off) 113 knots (130 m.p.h.) Vfe (Flaps landing) 106 knots (122 m.p.h.) Vmc (Minimum control) 50 knots ( 58 m.p.h.) Page 2 of 7 A29EU C.G. range (+20 in.) to (+25.6 in.) at 8,750 lb. (+21.0 in.) to (+25.6 in.) at 9,350 lb. Straight line variation between points. Empty weight C.G. range None Maximum weight 9,350 lb. Maximum takeoff weight. 9,350 lb. Maximum landing weight. 9,050 lb. Maximum zero fuel weight. Minimum crew One Pilot. Number of seats 18 (2 at -133.5 in) (2 at -103.4 in) (2 at - 74.1 in) (2 at - 45.7 in) (2 at - 15.9 in) (2 at + 14.2 in) (2 at + 43.5 in) (2 at + 71.5 in) (2 at +101.3 in) Maximum baggage 400 lb. (+144.0 in). Fuel capacity 196 U.S. gal. total (two 69 U.S. gal. main wing tanks at +27.0 in. plus two 29 U.S. gal. wing tip tanks at +34.0 in.) (See NOTE 1 for data on unusable fuel) Oil capacity 24 U.S. qt. total (two wing engines) (-2.6 in.) 12 U.S. qt. total (rear engine) (+164.5 in.) (See NOTE 1 for data on undrainable oil) Maximum Operating Altitude 12,000 ft. Control surface movements Wing flaps retracted Full Up 6° (down) Full Down 56° (down) Aileron Up 25° Down 15° Elevator Up 25 1/2° Down 19 1/2° Elevator trim tab* Up 23° Down 26° Rudder Right 20° Left 20° Rudder tab Right 20° Left 20° *(measured with elevator neutral) 2. Model BN.2A MK. III-2 Trislander, 18 PCLM (Normal Category), Approved December 9, 1976 (Same as BN.2A MK III except for elongated nose incorporating baggage compartment, increase in maximum weight and change in C.G. limits). Engines Three Lycoming O-540-E4C5 (See NOTE 6) Fuel 91/96 Minimum grade aviation gasoline Engine limits For all operations, 2700 r.p.m. (260 hp) Propeller and Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, Hartzell propeller limits HC-C2YK-2C/C8477-4, Hartzell HC-C2YK-2C/C8477A-4 and Hartzell HC-C2YK-2CF/FC8477A-4 (See Note 5). Diameter range 80" maximum, 78" minimum. No further reduction permitted. Pitch setting at 30 in. station: Low 12.5° High 78.6° Spinners: Hartzell 836-29 Governors: Woodward 210275, D210659, 210715, F210444, G210659, or B210715 (See NOTE 7) Airspeed limits (IAS) For operation in FAR Part 135 Category. (See NOTE 9 for FAR 91 operations) Vmo (Max. operating limit) 142 knots (164 m.p.h.) Va (Maneuvering) 133 knots (153 m.p.h.) Vfe (Flaps take-off) 133 knots (153 m.p.h.) Vfe (flaps landing) 110 knots (127 m.p.h.) Vmc (minimum control) 50 knots ( 58 m.p.h.) Page 3 of 7 A29EU C.G. range (+19 in.) to (+25.6 in.) at 8,750 lb. (See NOTE 9 for FAR 91 operations) (+19.6 in.) to (+24.95 in.) at 9,500 lb. Straight line variation between points. Empty weight C.G. range None Maximum weight 9,500 lb. Maximum takeoff weight, maximum landing weight, and maximum zero fuel weight. (See NOTE 9 for FAR 91 operations.) Minimum crew One Pilot. Number of seats 18 (2 at -133.5 in) (2 at -103.4 in) (2 at - 74.1 in) (2 at - 45.7 in) (2 at - 15.9 in) (2 at + 14.2 in) (2 at + 43.5 in) (2 at + 71.5 in) (2 at +101.3 in) Maximum baggage 300 lb. (-209.5 in) 400 lb. (+144.0 in). Fuel capacity 196 U.S. gal. total (two 69 U.S. gal. main tanks at +27.0 in. plus two 29 U.S. gal. wing tip tanks at +34.0 in.) (See NOTE 1 for data on unusable fuel) Oil capacity 24 U.S. qt. total (two wing engines) (-2.6 in.) 12 U.S. qt. total (rear engine) (+164.5 in.) (See NOTE 1 for data on undrainable oil) Maximum Operating Altitude 12,000 ft. Control surface movements Wing flaps retracted Full Up 6° (down) Full Down 56° (down) Aileron Up 25° Down 15° Elevator Up 25 1/2° Down 22 1/2° Elevator trim tab* Up 23° Down 26° Rudder Right 20° Left 20° Rudder tab Right 20° Left 20° *(measured with elevator neutral) 3. Model BN2A MK. III-3 Trislander, 18 PCLM (Normal Category), Approved February 9, 1977. (Same as BN2A MK. III-2 except for Autofeather system installation and increased weights). Engines Three Lycoming O-540-E4C5 (See NOTE 6) Fuel 91/96 Minimum grade aviation gasoline Engine limits For all operations, 2700 r.p.m. (260 hp) Propeller and Hartzell HC-C2YK-2B/C8477-4, HC-C2YK-2B/C8477A-4, Hartzell propeller limits HC-C2YK-2C/C8477-4, Hartzell HC-C2YK-2C/C8477A-4 and Hartzell HC-C2YK-2CF/FC8477-4 (See Note 5). Diameter range 80" maximum, 78" minimum. No further reduction permitted. Pitch setting at 30 in. station: Low 12.5° High 78.6° Spinner: Hartzell 836-29 Governor: Woodward 210521 or A210521 (See NOTE 8) Page 4 of 7 A29EU Airspeed limits (IAS) For operation to FAR Part 135 Category. (See NOTE 9 for FAR 91 operations) Vmo (Max. operating limit) 142 knots (164 m.p.h.) Va (Maneuvering) 133 knots (153 m.p.h.) Vfe (Flaps take-off) 133 knots (153 m.p.h.) Vfe (Flaps landing) 110 knots (127 m.p.h.) Vmc (Minimum control) 50 knots ( 58 m.p.h.) C.G. range (+19.0 in.) to (+25.6 in.) at 8,750 lb. (+20.0 in.) to (+24.5 in.) at 10,000 lb. Straight line variation between points. Empty weight C.G. range None Maximum weight 10,000 lb. Maximum takeoff weight. 10,000 lb. Maximum landing weight. 9,700 lb. Maximum zero fuel weight. Minimum crew One pilot. Number of seats 18 (2 at -133.5 in) (2 at -103.4 in) (2 at - 74.1 in) (2 at - 45.7 in) (2 at - 15.9 in) (2 at + 14.2 in) (2 at + 43.5 in) (2 at + 71.5 in) (2 at +101.3 in) Maximum baggage 300 lb. (-209.5 in) 400 lb. (+144.0 in). Fuel capacity 196 U.S. gal. total (two 69 U.S. gal. main tanks at +27.0 in. plus two 29 U.S. gal. wing tip tanks at +34.0 in.) (See NOTE 1 for data on unusable fuel) Oil capacity 24 U.S. qt. total (two wing engines) (-2.6 in.) 12 U.S. qt. total (rear engine) (+164.5 in.) (See NOTE 1 for data on undrainable oil) Maximum Operating Altitude 12,000 ft. Control surface movements Wing flaps retracted Full Up 6° (down) Full Down 56° (down) Aileron Up 25° Down 15° Elevator Up 25 1/2° Down 22 1/2° Elevator trim tab* Up 23° Down 26° Rudder Right 20° Left 20° Rudder tab Right 20° Left 20° *(measured with elevator neutral) DATA PERTINENT TO ALL MODELS Datum Wing leading edge (Stn. 234.5 in) Leveling means Fore and Aft leveling: Holes for datum pins on which straight edge is placed are located on the left side of the center fuselage. Lateral leveling: By a lateral leveling plate located on the cabin floor immediately forward of the aft baggage area (fuselage station 345). Page 5 of 7 A29EU Serial Numbers eligible The United Kingdom Certificate of Airworthiness for Export endorsed as noted under "Import Requirements" must be submitted for each individual aircraft for which application for certification is made. Import requirements A United States Airworthiness Certificate may be issued on the basis of a United Kingdom Certificate of Airworthiness for export signed by a member of the United Kingdom Department of Trade and Industry containing the following statement "The airplane covered by this certificate has been examined, tested and found to conform to the 14 CFR Part 23 approved under US Type Certificate A29 EU and is to be in condition for safe operation". Service Information Each of the documents listed below must state that it is approved by the United Kingdom Civil Aviation Authority (CAA) or – for approvals made between September 29, 2003 and December 31, 2020 – by the European Union Aviation Safety Agency (EASA). • Service bulletins, • Structural repair manuals, • Vender manuals, • Aircraft flight manuals, and • Overhaul and maintenance manuals. The FAA accepts such documents and considers the FAA -approved unless on of the following conditions exits: • The documents change the limitations, performance, or procedures of the FAA approved manuals: or • The documents make an acoustical or emissions change to this product’s U . S. type certificate as defined in 14 CFR 21.93. The FAA uses the post type validation procedures to approve these documents. The FAA may delegate on case -by-case to the United Kingdom CAA or – between September 29, 2003 and December 31, 2020 – to EASA, to approve on behalf of the FAA for the U.S. type certificate. If this is the case it will be noted on the document. Certification basis FAR 21.29 and FAR 23 effective February 1, 1965 as amended by amendments 23-1 through 23-9 inclusive, plus FAR 135 Appendix A, effective July 19, 1970 plus special conditions number 23-35-EU-7 issued August 4, 1971. Type Certificate No. A29 EU issued August 4, 1971 (re-issued to Britten-Norman, Bembridge, Limited on February 23, 1972). Date of application for Type Certificate, October 1, 1970. The United Kingdom CAA originally type certificated this aircraft under is type certificate Number BA 8. The FAA validated this product under U.S. Type Certificate number A29EU. Effective September 28, 2003, the EASA began oversight of this product on behalf of the United Kingdom CAA. Effective January 1, 2021, oversight of this product returned to the United Kingdom CAA. The United Kindom CAA issued TCDS UK.TC.A.00043 Issue 1 on September 5, 2022 that covers all BN2A MK. III models validated by the FAA. Validation basis Pursuant to FAR 21.29 (a)(1)(ii) Type Certificate No. A29 EU was issued in validation of the British Air Registration Board's certification of compliance with the following ` airworthiness standards which were found to provide a level of safety equivalent to that provided by the aforementioned type certification basis. 1. The British Certification Basis as stated in Air Registration Board Type Certificate Data Sheet No. BA.6 dated May 14, 1971. 2. The "FAA additional requirements for UK airplanes 12,500 lbs. or less Page 6 of 7 A29EU maximum weight" dated January 1, 1970. 3. FAR 23 Section 23.1529 effective February 5, 1970 (Amendment 23-8) and Section 23.1441, 23.1443, 23.1447 and 23.1449 effective June 17, 1970 (amendment 23-9). 4. FAR 135 Appendix "A" effective July 19, 1970. 5. FAA Special Conditions No. 23-35-EU-7 issued August 4, 1971. Equipment Basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following items of equipment are required: (a) Stall warning indicator (Safe Flight Type No. 165). (b) A pilot's rear view mirror installed on the forward L.H. fuselage. (c) Model BN.2A MK.III Trislander : CAA approved airplane Flight Manual, Document No. FM/BN.2A III/1, plus deviations 1 and 2 and subsequent CAA approved revisions. Model BN.2A MK.III-2 Trislander : CAA approved airplane Flight Manual, Document No. FM/BN.2A III/1, plus deviations 1, 2, and 16, and subsequent CAA approved revisions. For operations under FAR Part 91, Flight Manual supplement No. 17 applies. Model BN.2A MK III-3 Trislander : CAA approved airplane Flight Manual, document No. FM/BN.2A III/1, plus deviations 1, 2 and 16 and subsequent CAA approved revisions. For operations under FAR Part 91, Flight Manual supplement No. 18 applies. For compliance with FAR 135 Appendix A and associated Special Conditions, the following modifications must be incorporated. (a) Airspeed indicator marked to show a maximum operating limit speed (Vmo) Modification no. NB/M/610. (b) Rear engine fire detection system, Modification no. NB/M/508. (c) Rear engine power loss warning system, Modification NB/M/502 (Models BN-2A MK. III and BN-2A MK. III-2 only). (d) Auto-feather system to Modification NB/M/872 (BN2A MK. III-3 only). NOTE 1 : Current Weight and Balance report including list of equipment included in certificated empty weight and loading instructions where necessary, must be provided for each aircraft at the time of original certification. The certificated empty weight and corresponding center of gravity locations must include the following: - (a) 66 lb. of unusable fuel (42 lb. at +27.0 in and 24 lb. at +34.0 in). (b) 0 lb. undrainable oil. NOTE 2 : The following placards must be displayed on the instrument panel in full view of the pilot. "THIS AIRPLANE MUST BE OPERATED AS A NORMAL CATEGORY AIRPLANE IN COMPLIANCE WITH THE OPERATING LIMITATIONS STATED IN THE FORM OF PLACARDS, MARKINGS, AND MANUALS." In addition, all placards required in the applicable approved Airplane Flight Manual must be installed in the appropriate location. Also, each individual airplane must be fitted with a placard which specifies approved types of operations (such as V.F.R., I.F.R., day or night) to which the airplane is limited by the equipment installed. Page 7 of 7 A29EU NOTE 3 : RESERVED. NOTE 4 : Information essential for proper maintenance of the airplane is contained in the following Britten-Norman Limited documents: (a) Maintenance Manual, reference MM/2, dated 14th June 1971 or later revision. (b) Maintenance Schedule, reference MS/2 dated 18th June 1971 or later revision. NOTE 5 : Propellers of the type shown are eligible for the incorporation of Hartzell Service Bulletin 114 and Service Instructions No. 102. Propellers so modified have the letter U added to their type designation, e.g. HC-C2YK-2CUF/FC 8477A-1. NOTE 6 : Britten-Norman Modification NB/M/746 introduces the wide deck variant of the Lycoming O-540-E4C5 engine. There is no change in the engine type designation. Serial numbers of wide deck engines contain the identification letter "A" e.g. standard deck L-13268-48 becomes wide deck L-13268-48A. Britten-Norman Service Bulletin BN.2/SB.87 also refers. NOTE 7 : For aircraft fitted with wide deck engines (See NOTE 6), the only propeller governors to be fitted are: G210659 where no unfeathering accumulator is installed and B210715 where an unfeathering accumulator is installed. For the standard deck engines, propeller governor P/N D210659 and F210444 are interchangeable for aircraft without unfeathering accumulators and P/N 210715 and 210275 are interchangeable for aircraft with unfeathering accumulators. NOTE 8 : Propeller governor part numbers listed for BN.2A MK III-3 model Trislander are not interchangeable. P/N 210521 is applicable to standard deck Lycoming engines and P/N A210521 is applicable to wide deck engines. NOTE 9 BN.2A MK III-2 and -3 airplanes with modification NB/M/579 airspeed indictor installed are eligible for operation under FAR Part 91. Operations under FAR Part 91 must be conducted in accordance with the CAA approved airplane Flight Manual including the appropriate supplement as noted under equipment, paragraph (c), and the following data sheet information applies in lieu of that appearing under the corresponding heading for the particular model: Model BN.2A MK III-2 Airspeed limits (IAS) Vne (Never exceed) 182 Knots (210 MPH) Vno (Max structural cruising) 142 Knots (164 MPH) C.G. Range (+19.0 IN) to (25.6 IN) at 8750 LB. (+20.0 IN) to (24.5 IN) at 10,000 LB. Straight line variation between points. Maximum weight 10,000 LB. - maximum take-off weight 10,000 LB. - maximum landing weight 9,700 LB. - maximum zero fuel weight Model BN.2A MK III-3 Airspeed Limits (IAS) Vne (Never exceed) 182 Knots (210 MPH) Vno (Max. structural cruising) 142 Knots (164 MPH) ....END....